Convertible aircraft with jet-driven rotor



H. A. DE cENzo CONVERTIBLE AIRCRAFT WITH JET-DRIvEu-Ro'roa Filed Dfw.1v, 1952 i Feb. s, 41951 Sheets-Sheet 1 INVEN'ToR. Herbert-f A. DeCenzo.

' Feb. 5, 1957 H. A. DE :ENzo` 2,780,423

CONVERTIBLE AIRCRAFT wrm-1 JT-DRIVEN Ro'ToR Filed Dec. 17, 1952 i 8Sheets-Sheet 2 INVNTOR. Herber A. De Cenzo.

orney.

AMW"

Feb. 5, 1957" H. A. DE cl-:Nzo

CONVERTIBLE AIRCRAFT WITH JET-DRIVEN ROTOR Filed Dec. 17, 1952V1NVENToR. Herberz A. De Cenzo. BY'A` l e A Harney.

H. A. DE CENZO CONVERTIBLE AIRCRAFT WIIH JET-DRIVEN ROTOR Filed Dec. 17,1952 Feb. 5, 1957.

-8 Sheets-Sheet 4 I JNVENTOIL Herbefff '14. De Cenzo.

A Home).

Feb. 5, 1957 A H. A. DE cNzo 2,780,423

CONVERTIBLE AIRCRAFT WITH JET-DRIVEN ROTOR Hei-bed De Cer-:2o.V

A Homey.

Feb. 5, 1957 H. A. DE cENzo vCONVERTIBLE AIRCRAFT wm: JT-DRIVEN RoToRFiled Dec,v 17,1952

8 Sheets-Sheet 6 z z f/ lex, w

INVENTOR. Herberi A. De Cenzo. BY' A' Horney.

Feb. s, '1951 H. A. DE cENzo Y2,780,423 CONVERTIBLE AIRCRAFT w'ITHJET-DRIVENoToR Filed nee. 17, 1952 Aa sheets-she@ 7 192 l 22 K l22/ 22o/VJs 225 Feb. '5, v1957 H. A. DE cENzo v CONVERTIBLE AIRCRAFT WITHJET-DRIVEN RoToR s -sheets-slim a Filed Dec. 17', 1952 A INVENTOR.Herber! A. De Cenzo.

BY v v A orney.

United States Patent() 2,17 31914?? CONVERTIBLE AmCRAFT WITH JET-DRIVENi, i v l kleren* e .lle geese Arcadia Calif- {pplication December 17,1952, Serial No. 326,474

e? Claims tCl- 24er-o This invention has to do with an aircraft, and itis a general eldest {tl-.f 'the iilvelfitlelile 'Prevfle Simple,practical,A improved aircraft of the Lheayier than vair -type, and ofthe type that isconvertible -'to act either inthe nature of ahelicopteror as arediving'plane. Y 'i A itis' r'ceognizfed that aircraft `ofthetype including one or incre fired plant-Esci' Wings .hay'ece'rtaindesirable features and yet iare'lirnited by certain undesirablecharacteristics'. llt isV iikeyviseitrue that craiticharacterized byrotors and coinrnonly referred to ashelicopters have certain markedadvantages and are attended by other undesirable characteristics.`Proposals Inave been mardein thelnature o l craft combining features ofxed Wingle-lanes and helicopters; however;4 fortheniostfaartysuchconstructions are complex; expensive andinot'altogethcr satisfaddy orpactial; .i Y

itis a general object of this invention to provide lan aircraftctnve'rtiblfe to' act either as a fixed vWing glane or as a'helicopter,and 'posse "of such Vcornlainatiiin:1and arrangement and Ycnc-relationof lessential elenentsmas to forni a highly e'iiec'tive and practicalunitary structure.

' It is another object of this inventionto provide an aircraftl of thegeneral character referred to, characterized by one or more iet unitsservingwhen .in action to propel the 'craft forwarder horizontally',while at thesaine time delivering thegases that are utilized in thepropulsion of oneor vmore rotors employed primarily Vfor "vertical@eration lt'is another object of this invention to provide an aircraftof :the general character referred to, having armor, each blade offwhich is',plovicleldV With- AI"ropjelling unit, preferably at its youtere-n'djthe "propelling units"`being characterized by plugs or'closure'swhicm `v'vl'ien all in operation, streamline the rQtororsatisfactoryoperation as a plane or Wing, and which are selectivelyoperable ,to establish the rotor in condition 'for elfect'ive`depenl'iable jet operation. Y l another object o f this invention toprovidean aircr'a'lt of Vthe general character referred to includingasimple7 practical, 'ii `reve-d means by vvhicli the elements Oflllepropelling unite' tif 111e "eler'a'e dependeblyleentrolled from thebodyor fuselage'of ,tll'ecratt.` 'i it is a further object of this inventionto provide an aircraft of the' gelleral eheraeter `f ejfelrrell to,loreorae ing a simple, practical, irjnpro i Irotor rrioiinting'by4 whichthe rotor `is,jwhen employ das fa 'plane orblade, rdflglressed annexedYsentii/,e to ,th fu, lageqf thefcraftgand is, V'tt/'rien in operationas a rotor V d a sub antial distance of ``y"supperted ,to rotate freelythe fuselage and' is eiec about a suitable asis.`

lt is a further object of this invention to provvide an aircraft 'ofthe' general vcharacterreferred to, 'combining main or primary jet unitsat Vthe fuselage of 'the craft for forward propulsioh, aridjet units onthe 'rotors of the craft where after-burned ga'sesfr'oni the main Vjetuntsi'supjolernentedA by the introductionof "fuelf'serve t'o propeltherotors.

'It is a further object of this invention to provide an by line2,780,423 Patented Feb. 5, 1957 "ice ,atre the only parts of thevrotor'requiring movemeiitto gain both cyclic pitch and lcollectivepitch.

it is a-further object of this invention-to provide an aircraft of thegeneral character refw d toiv'vlierein there isagenerallirnproved'arangfneiitg coinbina,t iori,V andrelationship o fparts 4providing a siinplfe, pvracltiaL'itnproved construction thatiseasy ltooritrlV @11d lwhich is dependible and eiieetive in faction.

` PEhe Various Objects and IYfeatilires of `my invention ywill be-'fullyunderstood ffrorn the' following detailed descrip- Ltio lef e typicalPreferred' form' and applicjationnfmy invention, `j ro'ughout vvdescription Yreferencefis made to the aeedmpeyng dre es, itllwliich;

` f iiew ef .e vtreft .embodying the ntibn, the particular craftillustratedv being t "by two' 4rololte'steered longitudinally et thegreift, .and these rotets'in'tls fleure are illustrated ,in position toserve planes or Wings ofthe craft.

,Fle- ,2' .is an' enlarged detailed' transverse .Sectional flew YFig'fll is an enlarged ydetailed transversesectional view takensubstantially' as 'indicated by lineVrb-fi' on Fig', Figli is an'elargeddetailed transverse sectional Hvieri taken substantially 'as indicatedby line 5-'5 onFig'. 3. Fig. 6 is an"`enlarge`d detailed'plan sectionbfa portion of the structure,` being a vievv `taken substantially' as4inrdicatedby line 6 6 onFig. 3. Fig. 7 is an enlarged detailed verticalsectional Yview of a portion of the ystructure sh Wn in Fig. 2f; beinga'vievv takenfas indicatedby line 7 79171 .4 f y y ,i

Fig. 8 isanenlarged detailed sectional View of a p0rtionof the structures llovviii'n Fig.V 6, being a vievv talten es ,indiejefed byl'eeg en Eig- 46- .Fis- 9 leasenleraed detileel Seetieriel View ef e portie ef theStruetureel We i Fia! beina e View teken es indicated I-9 on Fig. v6,.

1,11 Pise 6 and 9; the parte ere Shewn .infull lines insee position'andare indicated by dotted lines in another position. v

.Fiel ,l0 iS en enlarged ,vertical detailed view 0f ,e portion ofthestructure as shown in Eig. 3, being atvifew illustrating in detail thestructure provided to mount a rotor from `the`fuselag`e of the craft,certain parts being broken avvay `to )show in section.

l Fig. `11 is an enlargeddetailed sectional view of a Dertien 0f theStruetre ,Shwn insliiel0, being a .View taken 'es indieated by line',1l-llos Flsl0." Eig- 12 is 'an enlarged detailed .sectional vievv'offaportion ,ofthe structure illustrated in Eig; l0, showing a detail ot aPressure generator 0r pump epelefed by the .mlerlFls- 13 is an enlargeddetailed sectional .viewer ia portion Qf theefrueture, being ,anenlarged detailed Section .taken substantially as indicated by the line?,'1 V11i). Fie 14 iS e plan elevation ,ef e .refer es' erevlsleslhy thepreeenflnveetien- Fia; 1.5 le en eel'erseslfid'etelled sectionalvieiv'fgafportion of the' struc ,shown 1n Fig.

1U, being La. viewtkeiias indicated by lineli-l-S" n Fig. 10. Fig. 16 isa detailed view of a portion of the structure shown in Fig. 15, being aview taken as indicated by line 16-16 on Fig. 15.

Figs. 17, 18, 19 and 20 are enlarged detailed transverse sectional viewsof the rotor as shown in Fig. 14, being views taken as shown by lines17-17, 18-18, 19-19 and Ztl-2t? respectively on Fig. 14.

Fig. 21 is an enlarged detailed plan section of a part of the structureshown in Fig. 17, being a view taken substantially as indicated by line21-21 on Fig. 17. Fig. 22 is a diagrammatic view illustrating the meansprovided for the shifting of the aps between retracted positions wherethey are, in effect, plane or wing forming parts of the rotor, and aworking or projecting position where they are supplemental to the bladesof the rotor to gain the pitching action desired.

Fig. 23 is a diagrammatic view illustrating a portion of the structureby which the aps and dampers at the blades of the rotor are operated insynchronism.

Fig. 24 is a diagrammatic View illustrating a part of the structure bywhich structure as indicated in Figs. 2l and 23 is operable from thefuselage of the craft; and Fig. 25 is a diagrammatic View illustrating apressure source and the operation of the shiftable elements of one ofthe rotor units from the fuselage of the craft.

The present invention contemplates various features of construction.various elements and relationships of parts, and numerous details whichare applicable generally to aircraft of the general type underconsideration. Since this is the case, the particular details set forthat this time and which will be hereinafter referred to are to beunderstood as merely typical embodiments of the invention, and it is tobe recognized that as the invention is applied to varying situations itmay be varied accordingly.

In the particular embodiment of the invention set forth in the drawingsthe structure includes generally a body or fuselage A which may, inpractice, be an elongate substantially rigid shell-like unit with a noseportion 10, a belly or middle portion 11, and a tail portion 12. Controlelements B are combined with or related to the fuselage A ascircumstances may require, and, in the case illustrated, they includeelements 13 at the tail portion 12 and elements 1.4 on limited wings 1Sthat project laterally from the sides of the middle portion 11 of thefuselage. It is to be understood that in practice, the controls may bevaried in number and character, and that their actuation can be effectedin any suitable manner.

The invention contemplates the provision of one or more rotors D inconnection with the fuselage A, and in the particular case illustrated,there are two rotors D which are substantially alike, and these arelocated at the upper portion of the fuselage and are spaced apartlongitudinally of the fuselage so that one adjoins the nose portionwhile the other adjoins the tail portion 12. So far as the presentinvention is eoncernedfthe essential features of construction and theequipment incidental to the rotors D may be alike, and therefore I willin the following description make reference to but one rotor, it beingunderstood that such description is equally applicable to both.

The present invention provides one or more jet units C on or inconnection with the fuselage A, and these are preferably direct-actingunits, for instance, they may be turbo jet units such as are commonly'employed in aircraft of the so-called jet type. In the particular caseas illustrated in Figs. 1 and 2, there are two jet units C and these arelocated at opposite sides of the fuselage and are it is to be observedthat at the forward ends of each unit C there is an air inlet 17, whileat the rear end thereof there is a rearwardly faced or opening nozzleportion 18.

A mounting means E carries each rotor D from the fuselage A for rotationabout a vertical axis and so that it is shiftable vertically relative tothe fuselage. In accordance with the invention as best shown in Figs.l() and 13, the mounting means E is a tubular structure adapted tohandle a substantial flow of hot gases from the fuselage A to the rotor,the blades of which are constructed to serve as conductors of suchgases. A duct F is provided in the fuselage A and serves to handle hotgases and to deliver them to the mounting means E for passagetherethrough to the rotor. In a preferred embodiment of the invention,the duct F is preferably located in the lower or bottom part of thefuselage as shown in Figs. 3 to 5, and extends longitudinally thereof,and, where there is more than one rotor and corresponding mounting meansE, it is preferred that there be a single duct F provided to supply hotgases thereto.

Gas receivers G are provided as shown in Figs. 3 and 4, it beingpreferred that there be at least one gas receiver G cooperativelyrelated to each jet unit C. The gas receivers G are adapted to receivehot gases issuing from the jet units C and to deliver such gases to theduct F for flow therethrough to the means E. In the particular caseillustrated, there is one gas receiver G for each jet unit C, and thereceivers are alike.

Rotor propelling units H are provided on or in connection with therotors D, preferably at the outer or tip end portions thereof, as shownin Figs. 14 and 17. In the particular case illustrated, there is onepropelling unit in connection with each blade of the rotor, and theunits H are at the outer extremities of the blades. `The propellingunits H are preferably of the jet type and are supplied with hot gasespassed by the mounting means E and conducted through the blades of therotor, the action of which hot gases may be supplemented by fuelsupplied to the units H by means I, which receives fuel at the fuselageand delivers it to the units H.

A means K is provided to supply electric energy from the fuselage A tothe units H as shown in Figs. 10 and 15, and a means L is provided toeffect operation of the working parts of the units H from the fuselage,the action of means L being best illustrated in the diagram Figs. 10 and25.

As illustrated in Figs. 18 to 20, each blade of the rotor is preferablyprovided with one or more aps M, and means N mounts the flaps on theblades of the rotors for pivotal movement and for shifting bodily fromretracted position where they fair into the airfoil contour of theblades and are tlush with the blades and working positions, where theyproject from the blades.

An ,operating means O illustrated diagrammatically in Fig. 22 of thedrawings is provided to actuate the means N and is preferablycoordinated with the means O so that the bodily shifting of the bladesmade possible by means N is coordinated with the operation of theworking parts of the means G and H.

The blades of the rotor are preferably provided at their upper forwardportions with slots 20, see Fig. 19, and variable area slot controls Pare provided and are preferably in the form of dampers. An operatingmeans Q is provided in connection with each flap M to operate or pivotit, while an operating means R is provided in connection with each slotcontrol or damper P.

A power means S is provided, as shown in Figs. 10, 13 and 24, to operatethe means Q and R simultaneously and in synchronism and so that thecoordinated flaps and dampers of one blade operate oppositely to thesearrangements of the other blade of the rotor.

A power means T is provided, as best shown in Figs. 3 and 13, to operatethe rotor vertically relative to the fuselage and a lock means U isprovided to secure the the `details about to be described( ln case ofthe fuselage A, it is contemplated that there mayv in practice be `aWideyar ri'formand construction. 'For the purpose of t presenti.rlivrention, yit ,may b e considered that fuselage a shell-lilrfejinitor structure characterized by V2'3 frame elements 2 4, other features of cr 1,struction Vsuch Vas are cornrlnorn to such a part fof the usualaircraft. "In the particular design illustrated, the l,fuselage :is Ianelongate h ollow shell vithfaf'top portion fZtfybottom 27 and sides`251.8. 1t is to be understood that these parts as they approach andterminate 1at the nose vportion 10 are suitably faired or related toprovide a suita'blyfround noseand likewise at the tail portion they ,arefaired relative to each other and `to the control parts V`that .areincorporated inthe structure. 'i

The .main jet units C as .provided y.by the present invention are theelements provided for .forward propulsion, and it is contemplatedthatinpractice v thleyrrnay be varied Vwidely in kformandconstruction,Vandthey `may belocated in various points V'on orrelativeto the fuselageas balance and sufficient propulsion Vmay require. In the Particularcase illustrated, .where there are two like .turbo jets C, `they arelocated at opposite Vsides of the middle portion 1 1 of the fuselage,aridetbey extend longitudinally of the fuselage sdih'af 'their ,aoailss1 8 pshgra'rvaly had are disposed t0 delirerfsts afectiva in.rfspsllihaths craft in a forward direction.

` .The rotor construction as providedby the present invention may bevaried widely and considerably. ,inthe particular caseillustrated, thegroter D is show-n as .asim- ,ple two-blade rotor, Awherein the two like.blades are d iamatriciana' ,opposite .each other cr weisst in oppositedirections from a `central portion or hub 3). The two blades .of the:rotar are preferably alike 0f identical, .eX- 'cept that they .are.nppositely dispuse@ .and histo he understood .that .in rra-Crise theyA:may he Yarihdwhsiderably as -t-o size, shape and length. in the caseillustrated, where the rot-oristo be Vemployed either as awing or planeAelement lof the vcraft or as a lift device, it -is preferred that each-blade be a 4*hollow shell-like .unit which is substantially rigid. lmthe .case illustrated, the blade construction involves top and bottomwalls 31 and 32 respectively, which have forward portions lthat convergeand which join at a'aleading edgeportionlv, while the rear edge portionsconverge and join at a ftrailing edge portion 34. in the particulardesign illustrated, the forward edge portions ofthe walls 31 and ,32`that join at the leading edge 33 `are similar generally in shape,whereas, in accordance with the present invention and to carry out themeans N hereinafter described, the rear edge portion 316 of the bottomwall is recessed or such as to establish -a cavity accommodating.elements of the means N andthe aps M as will be herein-after.described, whilethe rear-.edge portion 37 of the. top wallisofsimple,roundedformation, as clearly shown in Figs. 1 8, l1S? and of thedrawings.

The mounting means E provided by the present invention to carry therot-or D from .the fuselage A is best illustrated in Figs. l'OYand 13 ofthe drawings. ln general, the means E includes a .substantially verticaltubular column 49, sectional in formso thatibhasalowersection .41 .andan upper.sectionAZytelescopically rclatedjto the lower, section, andshiftable.vertically/relativothereto. A .means @zmount-s .meschina'th-fthe anlass A 91' limits? niv-gime usi/emes? 0r shifting relativ@thereto and vheretheicoliim fsect ional,` the nunt'ingmans .43 carriesthe flower section' `tfand serves to connect the lower end portioniofsection 41 to ythe fuselage. lA`tubular stem 'gld is fixed 'tothe hubportion`30 of the rotor and `depends therefrom into the yupper end ofthe upper section 4,2`of the column Afbearing rneans rotatably supportsthe stem 44 in the column section 42. An upper sealing' means ,46 seals'lbetween the stern and column-section 42, vwhile a lower 'sealing'means do@ seals between the stern 4 4 yand the columnfsection'di. Themountingmeansv 43 for -the column 4t) i s` 4such as to pro.

vide for or to allow rlimited pivotal shiftingor movement of the columnrelative to the fr isela'ge and therefore it is "preferred" lto providethe Vrneans with stabilizing VIn the preferred form 4of the invention,the telescopically related tubular sections 4,41- and 42 of the column4G .are of substantial size or diameter, and are wholly unretracted, sothat they cooperate with the .stern d4 to l provide a gasconductingstructureof ysubstantial capacity.

The mounting means 43 in the case illustrated, is shown as mounting thecolumn .dit on the top plate 50 which Vis .an lelement of the duct F 'aswill b e hereinafter described, the 4plate 5 0 being a fixed element inthe fuselage A and located in the lower 'portion thereof, Where it isVbut a short `distance above the bottom 27 of the fuselage. The mountingmeans E includesa ,tubular or annular base 51 XCd to lthe plate "50 asby means of fasteners 152 to be in register with a `port 53 provided inthe plateV 50. Ihebase 51 is ,provided with a circumferentially curvedseat 5 4. Ani yenlargement 55 `isp'rofvicled on the lower end portionsof fth'e'outfer column ,sec-

tion 4 1 and its x'terio'rSt is circumferentially'curved and en-gages in.the seat 5 4. retainer Yin the form of acolla'r 5;7 engages "aroundythe 4 enlargement 5 5Y and `a Serie's'io .circumferentially spaced tisf5.8v connect `the lrctainer SITandthebaSe'fSl so'that the retainerisheld engaged .the l enlargernerit 55 vand holds Vit engaged with the.seat 56. .Since structure just described is adapted -to handle gases,itis preferred in practicelto provide a gas-tight flexible vjacket 59around the elements justjdescribed, as clearly illustrated in Fig.1070i?` the dwings.. ,Y Y.

'lhe tubular stern lgis lined relative to .thehub por- 'tiah sith@ @forD and depends -thersfwfn is' @Xfhd :a Isubstantial*dist-ance Ldov.vnwardly of the upper end ofV the inner 'Sestsh ,4,2 0f .wlhmh fl@- ,Thebeating @sans 45 is preferably an antiffriction bearing means, 4servingto rotatably support lthe stem'l44 -in theupper section 42 of thecolumn. 4ln fthe particular construction illustrated, the bearin'gmeans4 5 includes an elongate series ofjantifriction-bearings 60 lin atubular vholder 6l carried in the column section 42' and ret-ainedby aremovable cap 62 Lheld in place by releasable fasteners 6 3. A tubularsleeve 6 4 tits around the stem 4 4 to dene Ian annular chamber 65 andit isxsupported on and is in etfcct made a part Iof the stern 44 bymeans of `flanges 66 projecting inward from the sleeveand engaging theexterior ofthe stem. A series ofbearings 60 isconfned-on `the sleeve 6 4between sLtQp la,1:iges,u"}' Through the construction justdescribed,.the stem is effectively supported in the upperfsection 42 Voflthe .column 40to .rotate freely relative thereto. i

,Suitable sealing means `are provided above and below thebearingmeans'l,as shown in Fig. 13. The upper sealingnreans 46 illustrated includesvallexible sealing member ,6 8l carried the stem and engageableiinthe cap62. 'A L l i The ,sealing means fllafbeyondthe lower end of the bea-ringincludes a labyrinth seal at`569, aflaip-type se a1 at 7,0, adap'aclging ati71.l i i In.the.preferredconstruetlom aliningyl .ofinsulating Wise therein to shield the bearing means from the heating ofgases carried by the stem.

A lubricating and cooling means is provided for bearing means 4S and inthe construction illustrated, a ilexible oil supply line 74 is connectedto the column section 42 to supply cool lubricant from a suitable sourcein the fuselage A to the lower end of the series of bearings 60. Thelubricant, after passing upward through the series of bearings, iiowsaround lthe upper end of the sleeve 64 to enter the annular chamber 65.A port conducts the lubricant from the lower end lof the chamber 65 to aIflexible discharge duct 76.

The stabilizing means 47 as provided by the present invention andillustrated in Figs. 3 and 6, includes a plurality of Vshock absorbingunits 80, anchored to suitable iixed supports S1 in the fuselage, andconnected to the upper end portion of the outer section 41 of column4t). In practice, the shock absorbers may be suitable hydraulic devicessuch as are commonly used in situations ot' this kind.

The stabilizing means 47 serves to normally hold thc column verticallydisposed, but not` solidly or rigidly. The action of the shock absorbers80 permits of, or allows for, certain limited movement of the column,relieving destructive strain from the craft.

The means T provided to operate the inner section 42 of the columnrelative to the outer section 41 is preferably a uid pressure actuatedmeans. As illustrated in Fig. 13, circumferentially spaced arms projectfrom the exterior of the column section 42 above the upper end 91 of theouter section 41. A cylinder and piston unit connects each arm with aflxed part of the fuselage or to the lower section 41 of the column. Inthe case illustrated, each of these uid pressure actuated units ormechanisms includes a cylinder 93 anchored to the exterior of the lowercolumn section by pin 94, while a piston 95 operates in the cylinder 93and is connected to an arm 90 by a rod 36. Suitable exiblefluid-handling ducts 98 connect to the ends of cylinder 93 andconnect'to a suitable reservoir and may, in practice, be under controlof a suitable valve.

As illustrated in Fig. l0, a spiing-actuated latch is carried by thelower section 41 of column 40 and when the upper section of the columnis in its down or retracted position, the latch enters an opening in theupper section 42 and thus serves to retain the column collapsed. ln theconstruction illustrated, the latch 100 is on a piston 101 in a cylinder102, and a spring 163 normally yieldingly urges the latch to operatingposition. The cylinder 102 is connected in the pressure supply line 98that connects to the lower end of cylinder 93, so that when pressure issupplied through said line 98 to cylinder 93 to move the column section42 upwardly, that pressure acts on piston 191 to release the latch 100.

The lock means U, as shown in Figs. l5 and 16, is adapted to lock thestem 44 projecting from the rotor to the upper section of the column 4)so that no relative rotation occurs between these parts. The lock meansU is a rcleasable device or mechanism and in the case illustrated itincludes a flange on the stern with a depending peripheral part having anotch 111 therein. A latch member 112 is mounted on the upper columnsection 42 to cooperate with the notched flange 110. In the caseillustrated, the construction includes a cylinder 113 mounted on cap 62to project upwardly therefrom. A stem 114 is carried by the cylinder andhas a head 115 engaged by a compression spring 116 in the cylinder. Thespring normally yieldingly urges the head upward. The latch 112 is onthe upper end of the stem 114 and is therefore normally yieldingly'heldup. The head 11S is in the nature of a piston slidable in the cylinder113, and the duct 118 to handle fluid under pressure connects to theupper end portion of cylinder 113. When fluid under pressure isintroduced into the upper end of cylinder 113 as through a suitablecontrol valve, the piston is moved downwardly and the latch 112 isreleased from the notched flange.

It is to be understood that in practice the parts just referred to arelocated or related so that when the latch 112 is engaged in the notch111 the rotor is in the desii-cd position relative to the fuselage, say,for instance, such as is illustrated in Fig. l of the drawings.

It is also to be understood that other means can be employed to preventthe rotation of the inner cylinder of the mounting means E, as forinstance, scissor structures, key and keyway structures, splines, andthe like.

In accordance with the present invention, the means T serving to effectmovement of the inner column section relative to the outer columnsection also serves as a means holding the column sections 41 and 42against relative rotation. ln the particular construction illustrated,the arms 96 of means T are not fixed directly onto the upper columnsection 42, but are on a collar 120, secured to the column section 42 bya screw thread. A iiuid pressure actuated motor 121 is iixed to thecollar 120 and is adapted to operate a worm 122 meshed with a gear 123on the column section 42. Through this construction, the motor 121 canbe energized to move the worm 120 one way or the other, and thus eiectadjustment or trimming of the rotor into the desired rotative positionrelative to the fuselage.

The duct F provided by the invention to occur in the fuselage is, in thecase illustrated in the drawings, established by the plate 50hereinabove referred to, and spaced vertical partitions 124 which extendbetween the plate 5i) and the bottom 27 of the fuselage A. In theconstruction illustrated, the plate 5l) is in effect a floor or falsebottom in the fuselage and the partitions 124 are parts which may servenot only to define the desired gas passage, but will also serve asstructural elements of the ship.

In the case illustrated, the plate 50 extends longitudinally of thefuselage and since there are two rotors with their mounting means E.,the plate 50 extends from one means E to the other. The partitions 124are coextensivc with the plate 50, and, as a result, there is alongitudinal flow passage 126 established in the fuselage at the bottomthereof as clearly shown throughout the drawings. As shown in Fig. 4,each gas receiver G is cooperatively related with or to a jet unit C,and in the case illustrated, it includes a tubular neck` 130, mountingmeans 131 mounting the neck in communication with the duct 126, a head132 on the neck of the upper end thereof, and provided with a forwardlyopening inlet port 136. A means 133 is provided for operating the neckto move it from a position within the fuselage to a position Where itprojects through an opening 134 in the fuselage so that the head 132with the inlet port 136 is in the path of gases issuing from the jetunit C.

In the case illustrated, the neck is a simple straight tubular part ofsubstantial size or capacity and when it is in the normal or retractedposition, as shown in Fig. 4, it is substantially vertical.

The mounting means 131 connects the lower end portion of neck 130 to theplato 50 so the neck is in co1nmunication with a port 137 in the plate50. in practice, the mounting means 131 is such as to provide for thedesired movement of the neck 130, as between the positions shown in fulland dotted lines in Fig. 4 of the drawings, and in construction, themounting means 131 may correspond to the means 43 hereinabove described,as will be observed from a comparison of Figs. 7 and l() of thedrawings.

The head 132 on the neck 130 at the upper end thereof is in the natureof a continuation of the neck projecting laterally therefrom, and firstlaterally of the fuselage and then forward, so that its terminal endfaces forward and at this point the head has the open inlet port 136.

The opening 134 provided in the side 28 of the fuselage is such as toallow for shifting of the head between the positions shown in full anddotted lines in Fig. 4, and it may havea hingedy closure 13S relatedthereto to close it when rnerneau, of the Yreceiver is'in` the fuselage,es. shown in f ull lines in Fig. 4. The operating means 133 ispreferably a liuidprossurc actuated means such, for example, as acylinder and piston mechanism as shown in the drawings, and suchmechanism may have one. end anchored inthe fuselage while the other endis connected to the head 132 as at 1,41, Suitable flexible lines orducts 142 may be connected to the. cylinder and piston mechanism, sothat operating lluid can be supplied thereto, so that when desired, theneck of the receiver is deected from the vertical position tolocate thehead inthe desired position relative to the jet unit C. lt will beobserved from the drawings that the head of the recelvrrvcan be locatedeither in4 a fully out position where G are passed thereby to the duct Fto flow therefrom through the mounting means E, which passes them to therotor D. t is also contemplated that the ducts 142 be `of what is knownin thetrade as the expanding and diffusingtype, so Ias to keep duct lossat a minimum.

in a` construction suh as is illustrated in Figs. l and 2 of thedrawings, where there is a jet unit C at each side of the fuselage,there may be two receivers G arranged side by side as shown in Figs. 4and 6 of the drawings, and suitable control valves incidental to theoperating means 133 may be provided so that the receivers can beoperated simultaneously or selectively as circumstances may require. Themeans V, as shown in Figs. 3 and 5, provided for checking or brakingforward movement of the craft is preferably carried by the fuselage A tobe located immediately behind the construction just described, it is,rearward of the gas receiver G.` Where there a jet unit at each sideofthe fuselage, it is preferred thatfthere be two units of means V, onerearward of each jet unit. In the case illustrated, the means V includesa flow-directing baille movable from a position within the fuselage as,shown in full lines in Fig. 5. toa position projecting fromthe fuselageas shown in dotted lines in 5. The baffle preferably passes r Operates',through an' Opening 146 provided in the side wall 2 8 of the fuselage.ln the form illustrated, the baffle includes a forwardly facing ridgeelement with lan edge 147. Cupishaped `or conf-v cave flow-directing cupportions 143 adjoin or extend from the two Vsides of the ridge 147 ,andare such that a rearwardly tiowing stream of gases hitting the baliedivided and deflected toestablish two forwardly directed streamsl ofgases spaced asubstantial distance apart. It is to be understood Vthatmore than two streams of gases could be established and if necessarydirected away from the fuselage so that overfheating of the fuselage bythe hot gases could, if necessary, be eliminated.

The means V includes suitable operating means `150 for the bafe 1,45 andin the case illustrated the meansf150`is auid maar@ assisted @sans 0r aCylinder andrisfse mechaism, Guust-ins. liliid. under suitable Comisi'is, supplied thereto by flexible ducts 151.

The present invention contemplates one or more rotor propelling units inconnection with rotor D and in a typical application, there is one rotorpropellingunit -Il-Ifiu connection with or carried by each blade of therotor; lna preferred. arrangement shown in Fig. i4, each rotorpropelling Vunit ifi `located at the outer or kterminalend of the bladewith which it is related, and the blade forms@ stsstabli 1 t@ `lia-le,sus. er; awrenasslgss serving to c'ondu t gases delivered to the to'tothe unit lu the Constructie illustrated. .nFisS- 1.3 and lil tato,

10 the blad@ 0f thermo! is presided.-infsrmeqiateits ,leading and;trailing. edge pgrfifns l'ud. 'rs'petiuy. W th@ internal raftitioni 169,Whsh'xtsl! longitud,... 1li Of; blade from the hub portion 30 ofthe'rotor to the unit H carried by the-blade. f'Thepart,itlQnS161) arespaced, apart andl define a central longitudinal passage 161 in theblade, a fsfward longitudinal passage 1,6% inl the blade, and a rearlongitudinal passage 163 'in the blade.4 In the preferred constructionthe hub portion. of' the. rotor is so conf structed as to exclude hotgases from the central passage 161, leaving this passage to handlecontrol elements, ducts 0f various kinds, and auxiliary equipment s maybev necessary. The passages 162 and 1,63 receivehot gases` at the hubportion 30v and conduct them longitudinallyY of the blade. Y

lt is to be understood that various blade constructions; can be employedto insureproper control of 'heat in the blades as between the ducts,and, might linclude insulated constructions, air-cooledconstruction orother like coil.-r structions. f v i The jet unit H atv theouter orterminal end of the, blade may in accordance with the broaderygninciplesl of the present invention be varied widely in form,construction and number. In the particular case illustrated in Figs. l4and 147, the unit Hy includes a tubularhousing portion 164 elongate inform and extending transverselyv of the blade at the terminal endthereof, and dening nozzles 165 facing fore and aft at the tip of theblade. The housing 164 defines a combustion chamber open to the nozzles16S.` A flame baille 16? confines combustion to the combustion chamberwhich is in communication with the nozzles while a duct '192 of means lsupplies fuel to the combustion chamber. An electric cable v169 extendsto the chamber to there energize an igniter 170. ln the constructionillustrated, ,plugs 18() are included in the means H, one for-orrelate'dto each nozzle 165. The plugs` are adapted to beV operatedsothat they both simultaneously close the nozzles 165, or they can beoperated to selectively close the nozzlesl so that one nozzle is openwhile the other is closed. In thel construction illustrated, each plugis carried by a ram 181 carried in a cylinder 1,82. The cylinder iscarried by a central support 1&3 and theV two cylinders for the twoplugs project in opposite directions from the support 183, one forward,the other aft. VSuitable'flexible lines 185 carrying operating fluid arepassed through the Vpassage 16.1.' w the Support .183. what# their are'connected to the cylinders 182l Aso that through operation of valvessuitably related to the lines 1 85 the rams` can be operated in eitherdirection to move the plugs l150 .between retracted positions where theyare clear'of ythe nozzles 165 and to extenqd positions where they closethe nozzles 165. Whse the elves 1.8i! are if; the Citaal position. theyprefer: ably have en d in )rt-ions` projectihgforward from and'beyond'thenoz'zle's, which fend'po ,ons aresuitably rounded andservetoeffecti ly s' -line the structure.

The means I, as shown rh rug. 154, provided'for supplyingthe fueltofiinit H .er to theseveral units H carried by the rotor preferablyincludes a flexible fuel Supply lille 19.1. .eX-wailing f1.1 @suitable@um Ofsurrlyi the insalate what?. theirs! be @der @and of .a valve, orthe like. 'fhev fuel line 2,591Y is connected t0. a fuel. lia@ i212Carried "bythe stoftllwagh 'a Coupling X. The particular coup 'ng-1X isva lslip'ring type devise. sa@ includa ist.. a'y uns 'latnfti with the,stern 4A, andspaced'fr'orh ring lll. .Sealing rings 19.5. Qf diligentdiameter so that they are saaie@ anat y seal between therings 1.913 and,and define 'an annular Chamber 19.6- 'lfinsrl 197th the ,fins 123Conducts f ul fre'm line 191m llu'chambsf 1%, 'while .a Suitable. 'P0Itin the ring 1196i condzuts fuel trein chamber 19.6

e the .feline i952? eans l provided for supplying ,electricV energylilies-lil@ assidus.

. 11 ring to the igniter 170. The slip-ring of means K is preferablycombined as a-unit with the coupling X of means I, and, as shown in Fig.15 of the drawings, the rings 193 and 194 carry cooperating contacts 202that serve to maintain electrical contact between the lines 200 and 169as the rotor operates.,

The means L is provided to eflect operation of the working parts orplugs of the unit H from the fuselage A. It is believed that the means Lwill be best understood from a consideration of. Fig. 25 of the drawingswhen this illustration is considered with Figs. l and 13 of thedrawings. It is contemplated that operating fluid under pressure,preferably air, is available at a suitable accumulator 210 located inthe fuselage A. The accumulator 210 may be supplied with air underpressure by means of a suitable power-driven pump 211 in the fuselage.

Where theI rotor has two blades, each with a jet unit H, the means Lpreferably includes two reversible control valves 21.5 in suitabletlexible fluid handling ducts ...i6 extending from the accumulator 210to the coupling X where parts or elements of the coupling form a part ofthe means L. In the coupling X the rings 193 and 194 with cooperatingsealing rings 195 provide fluid connections between the tluid handlingducts 216 in the fuselage, and fluid-handling ducts 217 in the rotor,which extend to the jet units H where the fluid serves to suitably`operate the iluid pressure actuated means handling the plugs 186. It ispreferred, in practice, that the valves 215 be connected or related as,for instance, by linkage 213, so that ordinarily the plugs are operatedso that those at the leading edge or leading nozzle of each bladeoperate in like manner, while those at the trailing edge or trailingnozzle operate in like manner, and the valving is preferably such thatit can be positioned so that the plugs are all simultaneously operatedto be in the out or nozzleclosing position.

The flaps M as provided by the present invention are preferably locatedat or related to the trailing edge portions of the blades, and in thecase illustrated in Figs. 14, and 18 to 20, the two tlaps occur at thetrailing edge portion of each blade. It is to be understood, however,that the number of ilaps may be varied, and in carrying out theinvention the several tlaps are preferably alike.

The means N mounts each flap on a blade of the rotor for movement orshifting between a retracted or inoperative position where the llap isbeneath the trailing edge portion of the blade and is adjacent theretoor llush therewith as shown in Fig. 18 of the drawings, and an operatingposition where it projects rearward of the blade and is free to betilted or swung to various positions as will be apparent from Figs. 19and 20 of the drawings.

In the case illustrated, the means N includes an element 220 which is ineffect a part or section of the blade itself and is shiftable relativeto the balance of the blade. In the construction illustrated, theelement or section 220 extends longitudinally of the blade and isco-extensive of the ap M that it supports. The element 220 is slidablyguided adjacent the flat lower trailing edge portion 36 of the blade tobe shiftable between a forward position as shown in Fig. 18 where itsexterior 221 forms a continuation of the exterior of the blade and arear or actuated position as shown in Fig. 19 where it is at the extremetrailing edge portion of the blade. In practice, suitable guides 122, orthe like, may be provided to support the element 220 for shiftingbetween the positions just referred to. In the preferred constructionthe tlap M carried by element 220 is joined thereto by a pivot pin 225,the axis of which is parallel with that of the blade, and the parts arearranged and related so that when the element 220 is retracted as shownin Fig. 18, the tlap is forward or retracted and its surface 226continues from the exterior surface 221 of element 220, and these partsform a continuation of the exterior of the blade, giving the blade anover-al1 desired cross-section as shown in Fig. 18. -When the parts arepositioned as shown in Fig. 19, the pivotal mounting ot the flap Mprovides for operation or shifting of the tlap to various positions aswill be apparent from Figs. 19 and 2() of the drawings.

- In accordance with the present invention, the means O provided toactuate the elements 226i between the positions above described, ispreferably a tluid pressure actuated means employing air and in the caseillustrated in Fig. 10, it preferably includes a single cylinder andpiston unit 230 serving to operate the several elements 221iincorporated in the blade construction. l'n the particular caseillustrated, and as will be best understood .from Fig. 22 of thedrawings, the cylinder 231 of the mechanism 230 is fixed, while thepiston 232 is adapted to be operated in the cylinder and carries anoperating rod 233 projecting from the ends of the cylinder. A system offlexible operating members or cables 235, shown in Fig. 22, connects toeach end of the rod 233, one system being for one blade of the rotor andthe other being for the other blade of the rotor. The flexible cables235 are trained and guided over pulleys 236 or the like, and suitablepulleys are coupled or related to the elements 220 so that operation ofthe mechanism 230 between two extreme positions serves to operate theelements 220 between the retracted and extended positions abovedescribed.

In practice, it is preferred that fluid-handling lines or ducts 233related to the fluid pressure actuated mechanism 230 be coupled with orrelated to ducts, for instance, lines 217 of means L, so that the meansO is operated in synchronism with the means L to the end that, when theplugs of the jet units H are operated by means L so that the rearwardlyfacing nozzles are open, the elements 22) are operated to the extendedposition shown in Fig. 19, placing the flaps in position for operation,whereas, when means L is positioned to close all of the nozzles of themeans H by means of the plugs, the eicments 220 are moved to theretracted position as shown in Fig. 18. Thus, when the rotor is set oradjusted to act as a rotor for controlling vertical action of the craft,the jet units H and the flaps are set for operation, whereas, when therotor is positioned relative to the fuselage so that it is stationaryand serves as a wing or plane, the structure at the means I-I is closedand streamlined and the flaps are retracted, giving the blades as awhole the desired configuration for planing action.

It is preferred, in practice, that lluid pressure actuated lock units300 be related to the rod 233 so that it is locked in its two extremepositions. Connectors such as lines 301 connect the locks in the tluidsystem so that, when pressure is applied to shift the rod, the lockholding it is released. This general arrangement will be understood fromexamination of Fig. 25 of the drawings.

In accordance with the preferred form of the invention, the blades ofthe rotor are provided in their upper forward or leading portions withslots 24d to provide construction for preventing or minimizing stallingsuch as is characteristic of helicopter operation. In the caseillustrated, in Figs. 18 to 20, each blade is provided with longitudinalslots 240 and the control means P for the slots provided by elements inthe form of dampers carried by pivotal mountings 241. When the rotor ist0 be used as a wing or planing element, the dampers are preferablyclosed as shown in Fig. 19, whereas, when the rotor is to be rotated,the dampers are preferably open,A as shown in Figs. 19 and 20. It is tobe observed that the construction is Such that the slots 240 are open toor are adapted to be supplied with gases from the forward passage 162 inthe blade. Further, it will be observed from the drawings, particularlyfrom the arrows in Fig. 19, how gases from passage 162 are handled bythe structure at the slots 240 to minimize stalling action.

The operating means Q, as shown in Fig. 2G, provided bythe presentinvention to effect tilting ot the flaps M preferably includes acorresponding means or construction in .connection withteach p,Athis.finlpraetice may include one or more-units involving a drive=sl1aft s260 carried bythe blade for-rotation, while anextension 261 ofthe .shaft 4.is telescopically vrelated `theretoand has keyed or,splined engagement therewith to `rotate with the shaft. AA worm262on`the .shaft Vextension A 261-rneshes With a gear segment 263 on the ap.From Fig. of the-drawings, it willbeapparentzthat as shaft 2k6tl isrotated,the ap M is-turned, deflected `or adjusted, and the structureis-such that the-flapcan be-moved-through a Widerange of adjustmentandLWillremain in any. position to Iwhich it `is adjusted .by reasons ofturning of shaft 269. l

The means rR providedfor v:operating each damper yP may include oneormore unitsincludinga `shiftable link 270 connected `to a togglemechanism 271 controlling operation `of Vthe damper. From Figrllof thedrawings, it will be apparentmthat.asithedink .2701s shifted lengthwise,thetoggle 271 is operated to move the damper between thepositionsshownin .Figs. 18 and `20.

The powery means Sprovided bythe present invention serves to .operatethe-means Q and R vinwsynchrorlisnrand is sueltas to resulti-nthewdesired cyclicpitching or feathering of the flap .orflapsin-synchronism with thedesired opening and closing -of the dampers,`to theend-that-th'e rotor as it turns has a highly desirable andefcientraction.

in the `case illustrated, it is,preferred that 4there be a unit ofmeansnQ oppositefor aligned witlra unit of means R -as shown inFig.20,.-and the power means S includes a rotatingvdrurn 28d related to eachcombination `of units of means Q andl. The drum 280 is rotatably mountedin the blade of `therotor vandcarriesa gear 281 meshed with a gear2SZonshaft26tl, sothat-as the drum turns the shaft 26d is rotated. Anyoperating screw .283 is threaded to the drumltleandis pivotallyconnected to the lin-lr 27d. As the .drumld turns, .theascrew .is movedlengthwise, causing shift-ing of the `link 270 to operate the togglemechanism 271.

The several drums 283 incorporated in a blade con-l struction of therotor are Coupled by a common line 29o, preferably a tlexible cablewhich is wound around each of the drums and which is suitably guided asby means of pulleys 291. This general construction is best illustratedin Fig. 23 of the drawings. A suitable means is provided in each bladefor operating the line 290 in the bladeiand in the case illustrated itis -shown as .apivoted quadrant 2% to 'which the ends of the lines 290are connected. The quadrant has a projecting .arm 294 and an operatingrod ZSS-connects to the arm 294.

It will be observed from Fig. l() ofthe drawings that the quadrant.291i`related toeach blade is mounted at the under `side ofthe-.blade:adjacent the hubportion of the rotor, while the operating line or cable29d extends through theblade in the chamber or passage 161. The means Sincludes structure by which the quadrants 293 are suitably oscillated,as the rotor turns, in order to gain the desired synchronousoperation-of the means Q and R operating the flaps M and dampers l. In theconstruction illustrated, `a collar 30d is-V supported on a bearingtltprovided on the upper end 4portion of the upper columnsection d2. Thebearing Stil has a spherical face carrying the 4collar ddii so that thecollar can :be

tilted or locked on .the bearing as by one or more operating units 3%2.in the case illustrated, several operating units 392 ,-preferablyhydrauhcally operated units, are circumferentially spaced about thestructure and `each has a cylinder-3533 Lpivote'd to al skirt Sil-ldepending from bearing 391 by means of .a` pvotpin 3%. A piston lincylinder tlcarries a `rod fitltdpivoted `to ,the collar 3%.@ by pivotpin 3d?. Fluid-handling lines 31d connect with the cylinder Sii?, and,in practice, are Vpreferably under control `of-a valve 33.1, so that asthe collar is moved or positioned up at one side of the structure, itispulled down at the .opposite side.

A sleeve 31th surrounds the collar Soil. and is supported The rods 29Sfrom .the two vcpiadrants'arrns 2393, thatis,

from vtheopposite -iblades,-connect to diametrically opposite ysides .ofthe sleevel When the collar 30G-and therefore the .sleeveSZis in acentral or unactuated position asishown in Fig. ri3, both quadrants 293are in thesarneposition, Whereas, when the collar is moved up at oneside and down at the other side, one quadrant 293 is operated in onedirection frornthe position 'shown in Fig. l0, While the other isoperated in the opposite direction from that position.

ln a ,preferred carrying out of the invention a second pair of.actuating unitsSQZa provided to tilt or rock the collar Stift Vonlbearing 3.91 is yincluded in the structure at right angles Vto lthepair of units 362 and is under control of a valve 311e. Byyproviding'two pairs of actuating units for rocking the collar 391i,accurate tilting ofthe collar can be gainedand-it is possible to locatethe collar in any desired tiltedposition about the pair.

in accordance with theconstruction provided by the invention, thebearing Sill surrounding the upper end portionrof the Luppercolumnsection i12-is slidable-longitu'dinally oncolumn section 42 to effectvertical shifting ot' the collarflitl .and its sleeve 3i to the end thatuniform general adjustment or shifting of the quadrants 29.3 can beeffected. VIn the construction illustrated, a plurality ofcircumferentially spaced actuating units 32() connect and operatebetween'the column section 42 and the bearingtl. in the caseillustrated, each actuating unit '32d may correspond .generally witheach unit 302 and so connects the bearing 3M with the sleeve-E asto-hold the bearing against turning on the column section While at the.Sametime being subject to operation to shift the hearing longitudinallyor vertically on the sleeve E. It rwill-be understood that suitablelluid pressure actuated mechanisms 3.20 supplied with operating fluidthrough lines 322i will eifect the desired action. rl`he How of lluid toand from theunits 326 may be under controlrot a suitable valve325,.'so'that an over-all or general adjustment of the iiap. and .damperaction of the rotor can be effected Whenever desired.

in carrying out the present invention, the tiuid pressurev actuatedsystem of means L is ypreferalzily separate from the luid ,pressureactuated.systemv .of the means S, and is `a pneumatic 4system-asdistinguished from the liquid system .employed `in .means S.

Fluid, such as oil, 4under pressure may be employed in :means Scandinthe draw-ings, a main pressurepunip 350 is shown supplying fa-receiver351 which supplies the necessary fluid under :pressure :in the linesor". meansS. ln the case illustrated, a second pump il?, -is driven as`the rotor operates and supplies oil under pressure to the receiver 551.in the case of the pump 2l2 driven from .the rotor, 4this pump may beVmounted onto the upper secton42 .ofcolurnn to be gear-'driven' Vby anelement rotating with the rotor,

.Fromthe foregoing .description it will be apparent that thepresentinvention provides a construction wherein the main jet units Care .serviceable to propel the craft forward wwhenthe Yrotors are xedrelative to the fuselage .andiserving as Wings or planes. Further, asthe rotors `are being turned so Vthat the craft acts as a helicopter,.the main jet units C can be operated so .that .part of. the ,gasestherefrom propel the -craft for Ward vWhile .the balance flows to' therotors for use at thejet .units H thereof, oiall of the gases from theunits C .can bepassed to the rotors. When the rotors are employed asplanes or wings the plugs ofthe units H closethe nozzles of rthe units Hand provide a satisfactory construction, and when the rotors zare 4inoperation ,.in .a normal manner, .the 'plugs .for the ynozzles at thetrailing-,edges vof the blades are retracted and the hotgases fedtoitheunitsv H. issue to etect propellinglof the rotors, and this actioncan be supplemented by fuel as desired.

It is to be understood that in carrying out the present invention, thevarious control devices, for instance, the valves, required, may inpractice be located convenient to the operator of the craft, and it isto be understood that various conventional construction or devices andany necessary auxiliary equipment incidental to an airplane or ahelicopter can be included in the structure as circumstances mayrequire.

Having described only a typical preferred form and application of myinvention, I do not wish to be limited or restricted to the specificdetails herein set forth, but wish to reserve to myself any variationsor modifications that may appear to those skilled in the art and fallwithin the scope of the following claims:

Having described my invention, l claim:

l. An aircraft including, an elongate fuselage, a jet type propellingunit carried by the fuselage and adapted to deliver gases rearwardly ofthe fuselage, a rotor carried by the fuselage on an axis transversethereof, and means adapted to receive gas delivered by the said unit andto deliver the received gas to the rotor including a gas receiverpivotally carried by the fuselage and means adapted to shift thereceiver relative to the said unit into and out of positioncooperatively related thereto.

2. An aircraft including, an elongate fuselage, a jet type propellingunit carried by the fuselage and adapted to deliver gases rearwardly ofthe fuselage, a rotor adapted to utilize gas, a tubular mounting carriedby the fuselage and rotatably supporting the rotor on an axis transverseof the fuselage, and means adapted to receive gas delivered by the saidunit and to deliver the received gas -to the mounting means for passagetherethrough to the rotor and including a gas receiver pivotally carriedby the fuselage and means adapted to shift the receiver relative to thesaid unit into and out of position cooperatively related thereto.

3. An aircraft including, an elongate fuselage having a side opening, ajet type propelling unit carried by the fuselage and adapted to delivergases rearwardly of the fuselage, a rotor carried by the fuselage on anaxis transverse thereof, and means adapted to receive gas delivered bythe said unit and to deliver the received gas to the rotor including agas receiver carried by the fuselage and adapted to shift relative tothe said unit into and out of position cooperatively related thereto,the receiver including an elongate tubular neck with a gas receivinghead at one end thereof and means pivotally supporting the other end ofthe neck whereby the neck is shiftable to operate the head in saidopening and relative to the said unit.

4. An aircraft including, an elongate fuselage having an opening andhaving a gas duct therein extending longitudinally thereof in the lowerportion thereof, a rotor above the fuselage, means mounted in thefuselage and adapted to receive gas from said duct and rotatablysupporting the rotor and adapted to deliver gas thereto, a jet typepropelling unit carried by the fuselage and delivering gases rearwardlythereof, and a gas receiver carried by the fuselage rearward of the saidunit, and adapted to receive the gases from the said unit and to deliverthem to the duct, the receiver including, an elongate tubular neck,means pivotally connecting one end of the neck and the duct so the neckextends upwardly therefrom, a forwardly opening head on the other end ofthe neck, and means adapted to operate the head through said opening andinto receiving engagement with said unit.

5. An aircraft including, an elongate fuselage, spaced jet typepropelling units carried by the fuselage and adapted to exhaust gasesrearwardly thereof, a rotor mounted on the fuselage on an axistransverse thereof, and means adapted to selectively receive the exhaustgases from said units and to deliver received gas to the rotorincluding, separate gas receivers pivotally carried by the fuselage, onecooperatively related to each jet unit and adapted to be varied relativethereto, and means adapted to shift the receivers to selectively operatethem into and out of receiving engagement with the said units.

6. An aircraft including, an elongate fuselage with an opening, a jettype propelling unit on the fuselage adapted to exhaust gases rearwardlythereof, and means adapted to receive gas delivered by said unitincluding, a tubular gas receiver with a forwardly opening portion, andmeans mounting the receiver from the fuselage for operation through saidopening to shift the said portion into receiving engagement with therear of the said unit.

7. In combination a fuselage, a rotor above the fuselage, and meansrotatably connecting the rotor and fuselage including, a substantiallyvertical tubular column having relatively movable upper and lowertelescopically related sections, means pivotally connecting the lowerend of the lower section to the fuselage, a tubular neck depending fromthe rotor and entered into the upper end of the upper section, and anantifriction bearing rotatably supporting the neck in the upper section.

8.111 combination a fuselage, a rotor above the fuselage, and meansrotatably connecting the rotor and fuselage including, a substaniallyvertical tubular column having upper aud lower telescopically relatedsections, means pivotally connecting the lower end of the lower sectionto the fuselage, a tubular neck depending from the rotor and enteredinto the upper end of the upper section, an anti-friction bearingrotatably supporting the neck in the upper section, and means adapted toshift the upper section of the column vertically relative to the lowersection to operate the rotor vertically relative to the fuselage.

9. ln combination, a fuselage, a rotor having an extensible flap adaptedto move and vary the area thereof, a mounting connecting the fuselageand rotor for relative movement about a vertical axis, the mountingincluding a tubular column carried by the fuselage and having relativelymovable upper and lower telescopically related sections, the lowersection being secured Ito the fuselage and the upper section rotatablysupporting the rotor, means whereby said flap is operated relative tothe rotor including, an element tiltably carried by the upper section ofthe column, and a shiftable member cooperatively related to the flap andcarried by the rotor in cooperative engagement with said elements, andmeans adapted to shift the upper section vertically relative to thelower sectron.

l0. ln combination, a fuselage, a slotted rotor having a damper adaptedto control the slot and having an cxtensible variable flap, a mountingconnecting the fuselage and rotor for relative movement about a verticalaxis, the mounting including a tubular column carried by the fuselageand rotatably supporting the rotor, and a single means whereby thedamper and llap are operated as the rotor turns relative to the columnincluding, an element tiltably supported by the columnand a membercooperatively related to the damper and flap and operated by saidelement.

ll. In combination, a fuselage, a slotted rotor having a damper adaptedto control the slot and having an extensible variable ap, a mountingconnecting the fuselage and rotor for relative movement about a verticalaxis, the mounting including a tubular column carried by the fuselageand rotatably supporting the rotor, operating means adapted to actuatethe damper, an operating means adapted to actuate the flap, and a singlemeans adapted to synchronously actuate said operating means responsiveto turning of the rotor relative to the column including, an elementtiltably supported by the column,

and ,El-member cooperatively relatedv to the damper and flap andoperatedby said element.

12; In combination, a fuselage, a slotted rotor, having a damper adaptedto control the slot and having an extensible variable flap, a mountingconnecting the fuselage and rotor for relative movement about a verticalaxis, the mounting including a tubular column carried by the fuselageand rotatably supporting the rotor, operating fuselage and rotatablysupporting the rotor, and a single means whereby the damper and flap areoperated as the rotorV turns relative to th@ column, includingi a'bearing on the column, a collar tiltable on the bearing, a sleeverotatably carried on the collar, and a shiftable; member carried byV therotor cooperatively related to the said operating means and adapted tobe actuated by: the sleeve.

14. ln combination, a fuselage, a slotted rotor havinga damper adaptedto` control the slot and havinganextensible variable llap, a mountingconnecting the fuselage and rotor for relative movement about a verticalaxis, the mounting including a tubular column carried by the-fuse; lageand rotatably supporting. the rotor, the column including telescopicallyrelated upper and, lower sections, the lower section being carried bythe fuselage, andthe upper section rotatablyl supporting'the-rotor,means adaptedV to shift VVthe upper section vertically relative tothelower section, and a single means whereby, the damperand flap are.operated as the rotor turns relative to the; column.

l5. In combination, a fuselage, a slotted rotor'having a damper adaptedto control the slot andhaving an extensible variable` llap, a mountingvconnecting the. fuselage and rotor for relative movement about avertical axis, the mounting including a tubular column carried byfthefuselage and rotatably supporting therotor, they column includingtelescopically related upper: and; lower sections, the lower sectionybeing. carried; by the fuselagesrand the upper sectionzrotatablysupporting-the rotor, meansadaptjed to shift the upper section;vertically relative to; the lower section, and-` a. singlemeans,\vher..eby the damper and flap` are. operated: as; the rotor turnsrelative to, the column, including, an element4 tiltably supported' bythe upper section. of` the column, and a membencooperatively relateditothe damper andlap and operatedby; said element3 16. ln combination, afuselage, a slotted'. rotor having a, damperadaptedto control;the:slot yand having a variable l'lap a. mounting. connecting-v the: fuselagevandi rotor for relative. movement; about.I a, vertical-r axis,; themount.- ing; including a. tubular column. carried by tbe fuselage and,rotatably supporting. the. roten. the column includ:- ing telesccpicallyrelatedupper. and lower. sections, the lower. sectionA beingcarried bytbefuselage and; the` upper section. rotatably` supporting. the foton.means. adapted to shift the` upper.l section. vertically relative to thelower section, anda singlemeans,` whereby tbealamper and flap are ioperated` as the.. rotor. turns relative. to thecolumn, including, abearing on: the-column, a.collar=tiltable;on the bearing, a sleeverotatably carriedlonthe-collar,l andra shiftable member carried by thelrotor, cooperatively related to thek saidl operating means and adaptedtoibe actuatediby the sleeve.

17.- In` combination, a. fuselage, a. slottedirotor hav.- ing. aidamperV adapted toicontrolt theslot'y andihavingda variable flap, aimounting connecting the; fuselage and rotor: for.. relative.V movementabout.` a vert-icaltaxisg. the

mountingincluding a tubularA column carried bythe fuselage and rotatablysupporting the rotor, the column including telescopieally related upperand lower sections, the lower'section being carried by the fuselage andthe upper section rotatably supporting the rotor, means adapted to shiftthe upper section vertically relative to the lower section, and a singlemeans whereby the damper and flap arevoperated asrthe rotor turnsrelative to the column, including, a. bearing on they upper section andshiftable longitudinally thereof, means adapted to shift said bearinglongitudinal of the upper section, a collar tiltable on said bearing,and a member carried by the rotor and cooperatively related to saidoperating means and adapted tothe operatedby said collar.

18. In combination, afuselage, a rotor having a blade, a substantiallyvertical column rotatably mounting the rotor on the fuselage, a ap,.anextensible mounting section` shiftably carried by theY blade andpivotally supportingv the ap, means whereby the mounting section isadaptedito be shifted and operable from the fuselage, and meanswhereby:the tlap ispivoted responsive to turning of therotor;

19; In combination, a fuselage, a rotor havingv a blade, a substantiallyvertical column rotatably mounting the rotorv on the fuselage, aiap,anextensible mounting secl tion shiftably carried by the blade andpivotally supporting the flap,` pneumatically actuated means whereby themounting` sectiony is adapted to be shifted and operable from thefuselage, and mechanically actuated means whereby the flap is pivotedresponsive to turning of the rotor.

2.0, In: combination, affuselage, a rotor havin-g a slotted blade, adamper at the' slotted portion of the blade,` a substantiallyverticalcolumn rotatably 'mounting the. rotor on the fuselage, a ap, anextensible mounting section shittably carriedL by tbe bladeandpi-votallysupporting the. flap,Y means whereby theymounting isadapted to be shifted and operable from the fuselage, and means wherebythe flap; and dampen are synchronously opera-tedV relativefto turningof: the rotor.`

21. lu combination-a fuselage, a rotor having aslotted blade az damperyat the slotted portion of the blade, a substantially vertiealtcolumnrotatably mounting-'the rotor on the, f uselageg; a ilap, a mountingshiftably carried by the bladeand pivotally-supporting the flap,pneumatically actuated means whereby the mounting is adapted. to beshifted andoperfable from thefuselage, and mechanically actuated.` meanswhereby, the flap and damper are synchronously operated relative to;turning of the rotor.

22. In,combinationa fuselage, a rotor havingablade, a,r substantiallyvertical column rotatably mounting the rotoronthefuselagma flap,ain-extensible mounting section., shiftably` carried, by the blade and pivotally supporting the flap, means whereby thev mounting section isadapted,v to be. shifted; andI operable from the fuselage,andmeanswherebyfthe flap is pivoted responsive toturning` of` therotor,including means adaptedI to oscillate the; flapand meansioperabletotvary-tbe-degree of oscillation V,ofthe ap:1'e1ative to the blade.

23,. In` combination, afuselage, a rotor having a blade; a substantiallyvertical column rotatablyI mounting the rotor on the fuselage; a flap,ai mountingv shiftably carrodlbythe-,blade and pivotallysupporting-theflap, means whereby. the: mounting isadapted to -beshifted: and operable,fr om, ther fuselage,v and means whereby the ap ispivoted responsive,- to turning of thev rotor, the column beingsectional ands including a lower tubularV section carried by.4 the:fuselage andv an upper tubular: ysection teleseopicallymelatedtothetlowersectionfand rotatably carryingthe rotor, v

2,4.. Incornbinatioma fuselage, a-rotorhavinga blade,- a. substantiallyvertical columnv rotatably mounting the rotor on the fuselage, a flap, amounting'shiftablycar;- riedgby; the;bladeandgpivotally;supporting; theiflap, means wherebyfthemountinggisadapted to bleishifted and operablefrom the fuselage, and means whereby the flap is pivoted responsive toturning of the rotor, the column including a lower tubular sectioncarried by the fuselage, an upper tubular section telescopically engagedwith the lower section and rotatably carrying the rotor, and meansadapted to operate the upper section vertically relative to the lowersection.

25. In combination, a fuselage, a rotor having blades, a mountingcarried by the fuselage rotatably carrying the rotor, jet propulsionnozzle units carried at the tips of the blades and including shiftablecontrol elements, flaps carried by the blades and adapted to shiftrelative thereto, and means adapted to synchronously operate the controlelements and flaps from the fuselage including a single fluid pressureactuated mechanism operating the several flaps and individual uidpressure actuated mechanisms operating the control elements.

26. In combination, a fuselage, a rotor having blades, an extensiblemounting section carried by the fuselage rotatably carrying the rotor,jet propulsion nozzle units carried by the tips of the blades andincluding shiftable control elements, flaps carried by the blades andadapted to shift relative thereto, and means adapted to synchronouslyoperate the control elements and aps from the fuselage including, a uidhandling slip-ring coupling at the mounting, a single fluid pressureactuated mechanism carried by the rotor and in communication with thecoupling operating the several aps, and individual fluid pressureactuated mechanisms at the propulsion units and in communication withthe coupling and operating the control elements.

27. In combination, a rotor blade, a jet propulsion unit on the bladeand including a shiftable control element, a flap, an extensiblemounting pivotally carrying the ap and shiftably supported on the blade,means adapted to oscillate the ap as the rotor turns, and means adaptedto synchronously operate the mounting and control element.

28. In combination, a slotted rotor blade, a slot damper, a jetpropulsion unit on vthe blade and including a shiftable control element,a flap, an extensible mounting section pivotally carrying the flap andshiftably supported on the blade, means adapted to oscillate the ap, andactuate the damper, as the rotor turns, and means adapted tosynchronously shift the mounting section and control element.

29. In combination, a slotted rotor blade, a slot damper, a jetpropulsion unit on the blade and including a shiftable control element,a flap, an extensible mounting section pivotally carrying the ap andshiftably supported on the blade, mechanical means adapted to oscillatethe ap and actuate the damper as the rotor turns, and iluid pressureactuated means adapted to synchronously shift the mounting section andcontrol element.

30. In combination, a rotor blade, a jet propulsion unit on the bladeand inclu-ding a shiftable control element, a flap, an extensiblemounting section pivotally carrying the ap and shiftably supported onthe blade, mechanical means adapted to oscillate the flap as the rotorturns, means adapted to synchronously shift the mounting section andcontrol element, and fluid pressure actuated means controlling the saidmechanical means.

3l. In combination, a fuselage, a rotor having a blade, a meansrotatably connecting the rotor and fuselage, a jet propulsion unit onthe blade and including a shiftable control element, a flap, anextensible mounting section pivotally carrying the Hap and shiftablysupported on the blade, mechanical means adapted to oscillate the flapas the rotor turns, means adapted to synchronously shift the mountingsectionrand control element, and a fluid pressure actuated control forthe said mechanical means carried by the means rotatably connecting therotor and fuselage.

32. In combination, a fuselage, a rotor having a blade, a mountingcarried by the fuselage and rotatably carry- Cil ing the blade, apropulsion unit on the blade and having a shiftable control part, aflap, an extensible member pivotally carrying the flap and shiftable onthe blade, means adapted to synchronously operate the said member andcontrol part, and means responsive to turning of thu rotor adapted tooscillate the flap.

33. In combination, a fuselage, a rotor having a slotted blade, a slotcontrol damper carried by the blade, a mounting carried by the fuselageand rotatably carrying the blade, a propulsion unit on the blade andhaving a shiftable control part, a flap, a member pivotally carrying theflap and shiftable on the blade, means adapted to synchronously operatethe said member and control part, and means responsive to turning of therotor adapted to oscillate the flap and operate the damper.

34. In combination, a fuselage, a rotor having a blade, a mountingcarried by the fuselage and rotatably carrying the blade, the mountingincluding a lower tubular section carried by the fuselage, an uppertubular section rotatably carrying the rotor and telescopically relatedto the lower section, and means adapted to shift the upper sectionrelative to the lower section, a propulsion unit on the blade and havinga shiftable control part, a flap, a member pivotally carrying the ap andshiftable on the blade, means adapted to synchronously operate the saidmember and control part, and means responsive to turning of the rotoradapted to oscillate the ap.

35. In combination, a fuselage, a jet unit carried by the fuselage, arotor having a blade, a mounting carried by the fuselage and rotatablycarrying the blade, a propulsion unit on the blade and having ashiftable control part, a ap, an extensible member pivotally carryingthe flap and shiftable on the blade, means adapted to synchronouslyoperate the said member and control part, means responsive to turning ofthe rotor adapted to oscillate the flap, and means adapted to receivegas from the jet unit and deliver it to the mounting for passagetherethrough and to the rotor for utilization at this propulsion unit.

36. In combination, a fuselage, a jet unit carried by the fuselage, arotor having a blade, a mounting carried by the fuselage and rotatablycarrying the blade, the mounting including a lower tubular sectioncarried by the fuselage, an upper tubular section rotatably carrying therotor and telescopically related to the lower section, and means adaptedto shift the upper section relative to the lower section, a propulsionunit on the blade and having a shiftable control part, a flap, a memberpivotally carrying the ap and shiftable on the blade, means adapted tosynchronously operate the said member and control part, means responsiveto turning of the rotor adapted to oscillate the flap, and means adaptedto receive gas from the jet unit and deliver it to the mounting forpassage therethrough and to the rotor for utilization at the propulsionunit.

37. In combination, a fuselage, a jet unit carried by the fuselage, arotor having a slotted blade, a slot control damper carried by theblade, a mounting carried by the fuselage and rotatably carrying theblade, a propulsion unit on the blade and having a shiftable controlpart, a ap, an extensible member pivotally carrying the ap and shiftableon the blade, means adapted to synchronously operate the said member andcontrol p-art, means responsive to turning of the rotor adapted tooscillate the ap and operate the damper, and means adapted to receivegas from the jet unit and deliver it to the mounting for passagetherethrough and to the rotor for utilization lat the propulsion unit.

38. In combination, a fuselage, a rotor having a tap adapted to moverelative thereto, a mounting connecting the fuselage and rotor forrelative movement about a ver- -tical axis, the mounting including atubular column carried by the fuselage and having upper and lowertelescopically related sections, the lower section being secured to thefuselage and the upper section rotatably supporting the rotor, meanswhereby said ap is operated relative to the rotor including, a bearingslidable along the upper section of the column, means adapted to operatethe bearing along the said upper section, a collar tiltably carried bythe bearing, and a member shiftably carried by the rotor andcooperatively related to the ap and adapted to be operated from thecollar as the rotor turns.

39. In combination a fuselage, a rotor above the fuselage, meansrotatably connecting the rotor and fuselage including, a substantiallyvertical tubular column having relatively movable upper and lowertelescopically related sections, means pivotally connecting the lowerend of the lower section to the fuselage, a tubular neck depending fromthe rotor and entered into the upper end of the upper section, ananti-friction bearing rotatably supporting the neck in the uppersection, and means whereby a lubricant is circulated to cool andlubricate the bearing.

References Cited in the file of this patent UNITED STATES PATENTS 22 lMyers Sept. 28, Maxwell June 15, Kloeren AJune 22, Pitcairn May 30,Stalker Jan. 3, Stalker Jan. 3, Doblhol Feb. 6, Herrick Mar. 6, DomanApr. 24, Harby Oct. 30, Youngman Ilan. 22, Douglas June 17, Bates Aug.12, Miller June 16, Dorand Sept. 1, De Cenzo Apr. 6,

FOREIGN PATENTS Great Britain July 9, Great Britain May 31, France Oct.31, Germany Sept. 17,

